Abstract: An aircraft engine, has: a pressure probe having: a static member having a front face and a back face, an inlet and an outlet fluidly connected to the inlet, the front face defining a curved surface; a movable member movably engaged to the static member and movable relative to the static member about a center of rotation, the movable member having a central axis, the movable member having an engagement section matingly engaged to the front face to slide against the curved surface, the engagement section having an opening, and an orientation section protruding from the engagement section and located rearward of the center of rotation, the orientation section defining an external surface exposed to the flow, wherein the movable member is movable relative to the static member as a result of a force imparted by the flow on the external surface.

Abstract: A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

Abstract: A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

Abstract: An improved approach for designing and verifying electronic designs at different levels of abstractions is disclosed. An electronic design undergoes high level verification, where the results of the high level verification can be guaranteed to be correct at the RTL level. This can be implemented by ensuring that model consistency rules are followed to generate high level (enhanced transaction level) models and/or RTL data. In this way, properties that are verified at one level of abstraction will not need to be re-verified at the other level of abstraction.